CN102748136B - The turbine blade stages in combustion gas turbine is used to carry out the equipment sealed - Google Patents
The turbine blade stages in combustion gas turbine is used to carry out the equipment sealed Download PDFInfo
- Publication number
- CN102748136B CN102748136B CN201210134178.6A CN201210134178A CN102748136B CN 102748136 B CN102748136 B CN 102748136B CN 201210134178 A CN201210134178 A CN 201210134178A CN 102748136 B CN102748136 B CN 102748136B
- Authority
- CN
- China
- Prior art keywords
- protective cover
- turbine blade
- outer protective
- interior
- blade stages
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000567 combustion gas Substances 0.000 title claims abstract description 33
- 230000001681 protective effect Effects 0.000 claims abstract description 174
- 239000007789 gas Substances 0.000 claims description 18
- 238000002485 combustion reaction Methods 0.000 claims description 9
- 239000000919 ceramic Substances 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 4
- 229910000753 refractory alloy Inorganic materials 0.000 claims description 4
- HPNSNYBUADCFDR-UHFFFAOYSA-N chromafenozide Chemical compound CC1=CC(C)=CC(C(=O)N(NC(=O)C=2C(=C3CCCOC3=CC=2)C)C(C)(C)C)=C1 HPNSNYBUADCFDR-UHFFFAOYSA-N 0.000 claims description 3
- 238000000746 purification Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims 2
- 238000003780 insertion Methods 0.000 claims 2
- 238000007789 sealing Methods 0.000 abstract description 2
- 238000001816 cooling Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 239000000112 cooling gas Substances 0.000 description 2
- 230000005489 elastic deformation Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- -1 and such as Substances 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Abstract
The present invention discloses the equipment that a kind of turbine blade stages used in combustion gas turbine carries out sealing.Described equipment includes that outer protective cover, described outer protective cover are connected to interior protective cover, and is configured to circumferentially around described turbine blade stages.Described interior protective cover is configured to circumferentially around described turbine blade stages, to use described turbine blade stages to seal, and include connecting element, described connecting element is configured to insert described outer protective cover, thus described interior protective cover is connected to described outer protective cover.
Description
Technical field
The present invention relates to combustion gas turbine, more precisely, relate to the efficiency improving combustion gas turbine
Technical field.
Background technology
Combustion gas turbine is known to us as the major impetus in power industry.In view of fuel
Price continues spiral escalation, therefore seeks new combustion gas turbine design, in order to improve its efficiency.
In gas-turbine unit, the turbine blade rotated in the turbine portion that temperature is higher
Can seal radially towards the part that the one of referred to as protective cover group temperature is higher.These protective covers are formed
Annular chamber, the turbine blade of rotation runs in described annular chamber.Annular chamber is formed and seals, should
Seal close but do not contact turbine blade, to avoid the combustion parts from combustion gas turbine
Steam dissipates around turbine blade.In prior art combustion gas turbine, these protective covers and/
Or it supports connector and generally has to by forcing air cooling to carry out forcing cooling.Cool down existing skill
Art protective cover adds the supplementary loss (parasitic losses) of gas turbine system, thus drops
The low whole efficiency of prior art gas turbine system.Therefore, if gas turbine system
In supplementary loss can reduce to increase its efficiency, then power industry the most gladly will accept this
Plant gas turbine system.
Summary of the invention
According to an aspect of the present invention, a kind of turbine being configured to use combustion gas turbine is disclosed
Machine leaf-level carries out the equipment sealed.Described equipment includes outer protective cover, and described outer protective cover is even
Receive interior protective cover, and be configured to circumferentially around described turbine blade stages.Described interior protective cover
It is configured to circumferentially around described turbine blade stages, close to use described turbine blade stages to carry out
Envelope, and includes connecting element, described connecting element be configured to insert described outer protective cover thus
Described interior protective cover is connected to described outer protective cover.
Described outer protective cover is configured to connect at least partly surround described combustion gas turbine
Housing.Described outer protective cover and described interior protective cover form chamber, and described chamber is configured to
The gas carrying out in described housing purifying cools down, and described chamber connects with described connecting element.Institute
State connecting element and include being provided with the flange in hole.Described outer protective cover is provided with hole, described Kong Jing
Configure, when described interior protective cover inserts described outer protective cover, to align what described flange was provided with
Hole.
Described equipment farther includes pin, and it is configured to insert what described outer protective cover was provided with
The hole that hole and described interior protective cover are provided with.Wherein, described alignment includes described outer protection
The hole that the hole that cover is provided with and described flange are provided with offsets a certain amount, thus inserts at described pin
Fashionable, described pin generation elastic deformation, so that described interior protective cover is pressed against described outer protective cover.
Described pin includes cone angle, and it is configured to described pin and inserts the hole that described outer protective cover is provided with
And described flange be provided with hole time, make described interior protective cover be pressed against described outer protective cover.
Described interior protective cover is provided with the space being positioned within described protective cover.The width in described space
Degree is more than the height in described space.Described interior protective cover includes that shaft of rib, described shaft of rib are arranged on institute
State in space, and be configured to increase the rigidity of described interior protective cover.Described outer protective cover includes
One or more engagement pads, it is configured to described interior protective cover and is connected to described outer protective cover
Time contact described interior protective cover.Described interior protective cover includes multiple interior protective cover part, each interior
Protective cover part is configured to be arranged adjacent to protective cover part in another, the most each interior anti-
Cover portion is circumferentially around a part for described turbine blade stages.Described interior protective cover is by pottery
At least one in based composites or refractory alloy is made, described ceramic matric composite or difficulty
Fusion gold is configured to bear the running temperature in described turbine blade stages.
According to a further aspect in the invention, a kind of combustion gas turbine, described combustion gas turbine are disclosed
Including: compressor section, it is configured to compress air inlet；Combustion parts, it is configured to combustion
Burn compression air inlet and fuel；And turbine portion, it includes turbine blade stages, described turbine
Machine leaf-level is configured to impact based on the steam from described combustion parts and rotates.Outer housing
Part is configured to circumferentially around described turbine blade stages, and is connected to interior protective cover.In described
Protective cover is configured to circumferentially around described turbine blade stages, to use described turbine blade stages
Sealing, and include connecting element, described connecting element is configured to insert described outer protection
Cover, thus described interior protective cover is connected to described outer protective cover.
According to a further aspect in the invention, a kind of gas turbine system, described combustion gas whirlpool are disclosed
Expander system includes the combustion gas turbine being connected to load.Described combustion gas turbine includes: turbine
Machine leaf-level；Outer protective cover, it is configured to circumferentially around described turbine blade stages；And it is interior
Protective cover, it is configured to circumferentially around described turbine blade stages to use described turbine blade
Level seals, and includes connecting element, and described connecting element is configured to insert described outer anti-
Guard shield, thus described interior protective cover is connected to described outer protective cover.Described combustion gas turbine system
System includes that housing, described housing are configured to connect to described outer protective cover, and at least partly wrap
Enclose described combustion gas turbine.Described gas turbine system includes cleaning system, described purification system
System is configured to use the purification gas purifying enclosure interior to purify described outer protective cover and institute
State one or more chambeies that interior protective cover is formed.
Wherein, described load is electromotor.
By following description and combine accompanying drawing and can clearly recognize these and other
Advantage and feature.
Accompanying drawing explanation
It is particularly pointed out by claims and clearly claimed the present invention.And pass through following description
Book also combines accompanying drawing it can be understood that the above-mentioned and other feature and advantage of the present invention, wherein
Similar elements has identical numbering, wherein:
Fig. 1 illustrates the sectional view of an exemplary embodiment of gas turbine system；
Fig. 2 illustrates the 3-D view of the protective acoustic cover assembly with outer protective cover and interior protective cover；
Fig. 3 illustrates the upward view of protective acoustic cover assembly；
Fig. 4 illustrates the 3-D view of interior protective cover；
Fig. 5 illustrates the side view of interior protective cover；
Fig. 6 depicts the details using the first method of attachment that interior protective cover is connected to outer protective cover
Aspect；
Fig. 7 depicts the details using the second method of attachment that interior protective cover is connected to outer protective cover
Aspect；And
Fig. 8 shows the 3-D view on the downside of outer protective cover, which depict for contacting interior protection
The liner of cover.
Detailed description of the invention part with reference to accompanying drawing with exemplary and non-limiting way explains this
Bright every embodiment and advantage and feature.
Component symbol list:
| Reference number | Parts | Reference number | Parts |
| 2 | Compressor section | 3 | Combustion parts |
| 4 | Turbine portion | 5 | Leaf-level |
| 6 | Turbine blade | 7 | Protective acoustic cover assembly |
| 8 | Turbine cylinder | 9 | Cleaning system |
| 10 | Gas turbine system | 11 | Combustion gas turbine |
| 12 | Electromotor | 13 | Axle |
| 20 | Interior protective cover | 21 | Outer protective cover |
| 22 | Groove | 23 | Pin |
| 30 | Interior protective cover part | 40 | Adpting flange |
| 41 | Hole | 50 | Shaft of rib |
| 60 | Hole | 80 | Engagement pad |
Detailed description of the invention
Fig. 1 shows the exemplary embodiment of gas turbine system 10.Described gas turbine
Machine system 10 includes combustion gas turbine 11, and it is connected to electromotor 12 via axle 13.Described
Electromotor 12 represents any load that can be provided power by combustion gas turbine 11, such as, is used for
Carry out aviation or mechanically operated blade load.Combustion gas turbine 11 includes: compressor section 2,
It is configured to compression and sucks air (air inlet)；Combustion parts 3, it is configured to burning pressure
The suction air of contracting and fuel；And turbine portion 4, it is configured to spontaneous combustion part in the future
The steam of 3 is converted into rotation function.Turbine portion 4 includes turbine blade stages 5, the most often
Individual level 5 is respectively provided with the multiple turbine blades 6 radially extended from axle 13.Circumferentially around each whirlpool
The protective acoustic cover assembly 7 being attached to turbine cylinder 8 of turbine blade level 5.Turbine cylinder
The inside of 8 is generally carried out in cooling air, and described cooling gas is used for purifying housing 8
Interior chamber.Cleaning system 9 uses cooling gas, and such as, air purifies housing 8.
Referring now to Fig. 2, which show and there is outer protective cover 21 and the protective cover of interior protective cover 20
Three-dimensional (3D) sectional view of assembly 7.Outer protective cover 21 is connected to housing 8 via groove 22.
Interior protective cover 20 uses multiple connecting pin 23 to be connected to outer protective cover 21.For manufacturing interior protection
The material of cover 20 can bear the higher running temperature in turbine portion 4, and without forcing
Cooling.Include that ceramic base is combined for manufacturing the non-limiting embodiments of the material of interior protective cover 20
Material (ceramic matrix composite materials) and refractory alloy.Interior protective cover
20 are provided with the space (void) being positioned within described protective cover 20.Described space has width
Degree W and height H.The sectional view of the interior protective cover 20 in embodiment illustrated in fig. 2 has substantially
On rectangle hollow shape and towards the bottom surface of the steam stream in turbine portion 4, and institute
State the end face of rectangular shape towards outer protective cover 21 and turbine cylinder 8.In interior protective cover 20
The advantage in space be, described space limits heat and passes from the bottom surface of interior protective cover 20
It is delivered to end face.It can be appreciated that outer protective cover 21 can be made by multiple sections.Fig. 2 illustrates one
Individual section.Fig. 3 is the top view of cover member 7, and wherein interior protective cover 20 includes multiple interior anti-
Cover portion 30, in these, protective cover part 30 constitutes interior protective cover 20.Fig. 3 show often
The bottom surface of individual interior protective cover part 30.
Fig. 4 illustrates the 3-D view of an interior protective cover part 30.Fig. 4 show one
The end face of interior protective cover part 30.Each interior protective cover part 30 includes one or more connection
Flange 40, described adpting flange 40 is configured to insert and be connected in described interior protective cover 21.
Each flange 40 in embodiment illustrated in fig. 4 includes hole 41, and it is configured to accommodate for entering
The pin 23 that row connects.Outer protective cover 21 includes opening, and it is configured to accommodate each connection method
Blue 40.Owing to the temperature of outer protective cover 21 is less than interior protective cover 20, therefore adpting flange 40
With the temperature of pin 23 less than the temperature of a part of interstitial interior protective cover 20, thus nothing
Need to cool down.
Fig. 5 illustrates the side view of an interior protective cover part 30.It is arranged on described interior protection
In cover part 30 is shaft of rib 50.Shaft of rib 50 is configured to increase interior protective cover part 30
Rigidity.
Fig. 6 illustrates the side view of the interior protective cover part 30 being connected to outer protective cover 21.
Pin 23 is by the hole 41 in adpting flange 40 and the hole 60 in outer protective cover 21, in hole
41 and hole 60 when aliging, interior protective cover part 30 is fixed to outer protective cover 21.A reality
Executing in example, in alignment procedure, hole 41 and 60 offsets, so that pin 23 occurs elastic shape
Become, to force interior protective cover part 30 to extrude outer protective cover 21.This design adjustable pin 23
Jib-length so that there is elastic deformation in pin 23, thus force interior protective cover part 30 to contact
Outer protective cover 21, the stress in protective cover part 30 in thus reducing.Fig. 6 also show shape
Become an example in chamber in protective acoustic cover assembly 7.This chamber and adpting flange 40 and pin 23
It is being carried out for purifying in the cooling air within housing 8.It can be appreciated that this chamber provides
Another example of a kind of connection scheme, this scheme is without by special pressure air cooling source
Carry out forcing air cooling.
Fig. 7 illustrates a kind of alternative that interior protective cover part 30 is fixed to outer protective cover 21
Method.In the embodiment shown in fig. 7, pin 23 includes cone angle, and it is configured to pin 23 and inserts
Force interior protective cover part 30 against outer protective cover 21 during hole 41 and 60.In this design makes
Protective cover part 30 deforms, to keep contacting with outer protective cover 21, but also can inside protective cover
Part 30 increases stress.
Fig. 8 illustrates the 3D upward view of outer protective cover 21.In the embodiment shown in fig. 8, outward
Protective cover includes engagement pad 80, and it is configured to interior protective cover part 30 and is connected to and is pressed against
The protective cover part 30 in contact when outer protective cover 21.One advantage of engagement pad 80 is,
It connects produced power can be directed to the region of outer protective cover 21, described outer protective cover 21
Region the most firm, it is sufficient to accept these power without being damaged or deforming.Engagement pad 80
Another advantage is that, the spatial loop between interior protective cover part 30 and outer protective cover 21 around
Engagement pad 80 and formed.This space as insulating portion with limit heat from interior protective cover part
30 are delivered to outer protective cover 21, thus keep the temperature of outer protective cover 21 less than interior protective cover portion
Divide the temperature of 30.
It can be appreciated that the exemplary embodiment disclosed in this specification is because of the operation of auxiliary equipment
Decrease the supplementary loss in gas turbine system, and therefore add the whole of combustion gas turbine
Body efficiency.
Article "a" or "an" is used to introduce the element of every embodiment.Described article purport
One or more described element is there is in expression.Term " includes " and " having " is intended to indicate that
Inclusive implication, thus represent in addition to listed element to also have other elements.Conjunction "or"
Any of which term or term combination it is intended to indicate that with one group of at least two term when being used together.
Term " first " and " second " are used for distinguishing each element, and are not intended to indicate specific suitable
Sequence.Term " connects " and relates to parts and be directly connected to another parts, or via one
Or multiple intermediate member is connected indirectly to another parts.
Although this specification describes the present invention in detail only in conjunction with the embodiment of limited quantity, but should
Understanding, the present invention is not limited to these embodiments disclosed.On the contrary, the present invention may be modified to
Contain all before the most do not introduce but the change, more that is consistent with the spirit and scope of the present invention
Change, replace or equivalent.Although additionally, describe various embodiments of the present invention, but should
Understanding, each aspect of the present invention can only include some embodiments in previous embodiment.Therefore,
The present invention is not construed as being limited by aforementioned specification, and it is limited only by the following claims scope
Restriction.
Claims (8)
1. one kind is configured to use the turbine blade stages (5) of combustion gas turbine to seal
Equipment, described equipment includes:
The housing of combustion gas turbine；
Outer protective cover (21), it is configured to circumferentially around described turbine blade stages (5), described
Outer protective cover (21) is configured to connect at least partly surround the housing of described combustion gas turbine；And
Interior protective cover (20), it is configured to circumferentially around described turbine blade stages (5) to use
Described turbine blade stages (5) seals, and includes connecting element, described connecting element warp
It is configured for insertion into described outer protective cover (21) thus described interior protective cover (20) is connected to described
Outer protective cover (21), described interior protective cover is provided with the space being positioned within described protective cover；
Wherein, described outer protective cover (21) and described interior protective cover (20) form chamber, described chamber warp
Configuration cools down with the gas by carrying out purifying in described housing, and described chamber is connected with described
Element connects.
Equipment the most according to claim 1, it is characterised in that described connecting element includes it
In be provided with the flange of the first hole (41).
Equipment the most according to claim 2, it is characterised in that described outer protective cover (21)
Being provided with the second hole (60), described second hole (60) is configured to described interior protective cover (20) and inserts
When entering described outer protective cover (21), the first hole (41) that the described flange that aligns is provided with.
Equipment the most according to claim 3, it is characterised in that farther include pin (23),
It is configured to insert the second hole (60) that described outer protective cover (21) is provided with, and is arranged at
First hole (41) of the described connecting element on described interior protective cover (20).
Equipment the most according to claim 1, it is characterised in that described interior protective cover (20)
Including multiple interior protective cover (20) parts, each interior protective cover (20) part is configured to be arranged to neighbour
Closely protective cover (20) part in another, the most each interior protective cover (20) is partially circumferentially around described
A part for turbine blade stages (5).
Equipment the most according to claim 1, it is characterised in that described interior protective cover (20)
It is made up of at least one in ceramic matric composite or refractory alloy, described ceramic matric composite
Or refractory alloy is configured to bear the running temperature in described turbine blade stages (5).
7. a combustion gas turbine (11), including:
Compressor section (2), it is configured to compression and sucks air；
Combustion parts, it is configured to burning compression and sucks air and fuel；
Turbine portion (4), it includes turbine blade stages (5), described turbine blade stages (5)
It is configured to impact based on the steam from described combustion parts (3) and rotates；
The housing of combustion gas turbine；
Outer protective cover (21), it is configured to circumferentially around described turbine blade stages (5), described outside
Protective cover (21) is configured to connect at least partly surround the housing of described combustion gas turbine；And
Interior protective cover (20), it is configured to circumferentially around described turbine blade stages (5) to use
Described turbine blade stages (5) seals, and includes connecting element, described connecting element warp
It is configured for insertion into described outer protective cover (21) thus described interior protective cover (20) is connected to described
Outer protective cover (21), described interior protective cover is provided with the space being positioned within described protective cover；
Wherein, described outer protective cover (21) and described interior protective cover (20) form chamber, described chamber warp
Configuration cools down with the gas by carrying out purifying in described housing, and described chamber is connected with described
Element connects.
8. a gas turbine system (10), including:
Combustion gas turbine (11), comprising: turbine blade stages (5)；Outer protective cover (21),
It is configured to circumferentially around described turbine blade stages (5), and described outer protective cover (21) is configured to
It is connected at least partly surround the housing of described combustion gas turbine；And interior protective cover (20), it is joined
It is set to circumferentially around described turbine blade stages (5) to use described turbine blade stages (5) to enter
Row seals, and described interior protective cover is provided with the space being positioned within described protective cover, and includes even
Connecing element, described connecting element is configured to insert described outer protective cover (21) thus by described interior
Protective cover (20) is connected to described outer protective cover (21), wherein, described outer protective cover (21) and institute
Stating interior protective cover (20) and form chamber, described chamber is configured to purify in described housing
Gas cool down, described chamber connects with described connecting element；
Load, it is connected to described combustion gas turbine；
Housing, it is configured to connect to described outer protective cover (21), and at least partly surrounds institute
State combustion gas turbine；And
Cleaning system (9), it is configured to use the purification gas purifying described enclosure interior
Purify described outer protective cover (21) and one or more chambeies that described interior protective cover (20) is formed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/088635 | 2011-04-18 | ||
| US13/088,635 US8998565B2 (en) | 2011-04-18 | 2011-04-18 | Apparatus to seal with a turbine blade stage in a gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102748136A CN102748136A (en) | 2012-10-24 |
| CN102748136B true CN102748136B (en) | 2016-12-14 |
Family
ID=45999652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210134178.6A Active CN102748136B (en) | 2011-04-18 | 2012-04-18 | The turbine blade stages in combustion gas turbine is used to carry out the equipment sealed |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8998565B2 (en) |
| EP (1) | EP2527599B1 (en) |
| CN (1) | CN102748136B (en) |
Families Citing this family (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9726043B2 (en) | 2011-12-15 | 2017-08-08 | General Electric Company | Mounting apparatus for low-ductility turbine shroud |
| BR112015028691A2 (en) | 2013-05-17 | 2017-07-25 | Gen Electric | housing support system |
| EP3080403B1 (en) | 2013-12-12 | 2019-05-01 | General Electric Company | Cmc shroud support system |
| JP6574208B2 (en) | 2014-06-12 | 2019-09-11 | ゼネラル・エレクトリック・カンパニイ | Shroud hanger assembly |
| WO2015191169A1 (en) | 2014-06-12 | 2015-12-17 | General Electric Company | Shroud hanger assembly |
| CN106460542B (en) | 2014-06-12 | 2018-11-02 | 通用电气公司 | Shield hanger component |
| CA2955121C (en) | 2014-06-12 | 2019-10-01 | General Electric Company | Shroud hanger assembly |
| US9874104B2 (en) | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
| US10132197B2 (en) * | 2015-04-20 | 2018-11-20 | General Electric Company | Shroud assembly and shroud for gas turbine engine |
| US10370997B2 (en) * | 2015-05-26 | 2019-08-06 | Rolls-Royce Corporation | Turbine shroud having ceramic matrix composite seal segment |
| US9963990B2 (en) | 2015-05-26 | 2018-05-08 | Rolls-Royce North American Technologies, Inc. | Ceramic matrix composite seal segment for a gas turbine engine |
| US10221713B2 (en) | 2015-05-26 | 2019-03-05 | Rolls-Royce Corporation | Shroud cartridge having a ceramic matrix composite seal segment |
| US10370998B2 (en) | 2015-05-26 | 2019-08-06 | Rolls-Royce Corporation | Flexibly mounted ceramic matrix composite seal segments |
| US10087770B2 (en) * | 2015-05-26 | 2018-10-02 | Rolls-Royce Corporation | Shroud cartridge having a ceramic matrix composite seal segment |
| EP3121387B1 (en) * | 2015-07-24 | 2018-12-26 | Rolls-Royce Corporation | A gas turbine engine with a seal segment |
| US9945244B2 (en) * | 2015-08-13 | 2018-04-17 | General Electric Company | Turbine shroud assembly and method for loading |
| US9903218B2 (en) | 2015-08-17 | 2018-02-27 | General Electric Company | Turbine shroud assembly |
| US10100654B2 (en) | 2015-11-24 | 2018-10-16 | Rolls-Royce North American Technologies Inc. | Impingement tubes for CMC seal segment cooling |
| US10132194B2 (en) | 2015-12-16 | 2018-11-20 | Rolls-Royce North American Technologies Inc. | Seal segment low pressure cooling protection system |
| US10746037B2 (en) | 2016-11-30 | 2020-08-18 | Rolls-Royce Corporation | Turbine shroud assembly with tandem seals |
| US20180355754A1 (en) * | 2017-02-24 | 2018-12-13 | General Electric Company | Spline for a turbine engine |
| US20180340437A1 (en) * | 2017-02-24 | 2018-11-29 | General Electric Company | Spline for a turbine engine |
| US10480337B2 (en) | 2017-04-18 | 2019-11-19 | Rolls-Royce North American Technologies Inc. | Turbine shroud assembly with multi-piece seals |
| CA3000376A1 (en) * | 2017-05-23 | 2018-11-23 | Rolls-Royce Corporation | Turbine shroud assembly having ceramic matrix composite track segments with metallic attachment features |
| US10619514B2 (en) | 2017-10-18 | 2020-04-14 | Rolls-Royce Corporation | Ceramic matrix composite assembly with compliant pin attachment features |
| US10801350B2 (en) | 2018-02-23 | 2020-10-13 | Rolls-Royce Corporation | Actively cooled engine assembly with ceramic matrix composite components |
| US11255209B2 (en) * | 2019-08-29 | 2022-02-22 | Raytheon Technologies Corporation | CMC BOAS arrangement |
| US11041399B2 (en) * | 2019-11-01 | 2021-06-22 | Raytheon Technologies Corporation | CMC heat shield |
Family Cites Families (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3656862A (en) * | 1970-07-02 | 1972-04-18 | Westinghouse Electric Corp | Segmented seal assembly |
| US4247248A (en) * | 1978-12-20 | 1981-01-27 | United Technologies Corporation | Outer air seal support structure for gas turbine engine |
| US4337016A (en) * | 1979-12-13 | 1982-06-29 | United Technologies Corporation | Dual wall seal means |
| GB2117843B (en) * | 1982-04-01 | 1985-11-06 | Rolls Royce | Compressor shrouds |
| US5080557A (en) | 1991-01-14 | 1992-01-14 | General Motors Corporation | Turbine blade shroud assembly |
| FR2766517B1 (en) * | 1997-07-24 | 1999-09-03 | Snecma | DEVICE FOR VENTILATION OF A TURBOMACHINE RING |
| EP1124039A1 (en) * | 2000-02-09 | 2001-08-16 | General Electric Company | Impingement cooling apparatus for a gas turbine shroud system |
| US6877952B2 (en) * | 2002-09-09 | 2005-04-12 | Florida Turbine Technologies, Inc | Passive clearance control |
| US6758653B2 (en) | 2002-09-09 | 2004-07-06 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
| US9068464B2 (en) | 2002-09-17 | 2015-06-30 | Siemens Energy, Inc. | Method of joining ceramic parts and articles so formed |
| US6821085B2 (en) * | 2002-09-30 | 2004-11-23 | General Electric Company | Turbine engine axially sealing assembly including an axially floating shroud, and assembly method |
| US7044709B2 (en) * | 2004-01-15 | 2006-05-16 | General Electric Company | Methods and apparatus for coupling ceramic matrix composite turbine components |
| US20060078429A1 (en) | 2004-10-08 | 2006-04-13 | Darkins Toby G Jr | Turbine engine shroud segment |
| US7563071B2 (en) | 2005-08-04 | 2009-07-21 | Siemens Energy, Inc. | Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine |
| US7556475B2 (en) | 2006-05-31 | 2009-07-07 | General Electric Company | Methods and apparatus for assembling turbine engines |
| US7950234B2 (en) | 2006-10-13 | 2011-05-31 | Siemens Energy, Inc. | Ceramic matrix composite turbine engine components with unitary stiffening frame |
| US7722317B2 (en) | 2007-01-25 | 2010-05-25 | Siemens Energy, Inc. | CMC to metal attachment mechanism |
| GB0703827D0 (en) * | 2007-02-28 | 2007-04-11 | Rolls Royce Plc | Rotor seal segment |
| US7811054B2 (en) * | 2007-05-30 | 2010-10-12 | General Electric Company | Shroud configuration having sloped seal |
| US8061977B2 (en) | 2007-07-03 | 2011-11-22 | Siemens Energy, Inc. | Ceramic matrix composite attachment apparatus and method |
-
2011
- 2011-04-18 US US13/088,635 patent/US8998565B2/en active Active
-
2012
- 2012-04-05 EP EP12163448.9A patent/EP2527599B1/en active Active
- 2012-04-18 CN CN201210134178.6A patent/CN102748136B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| US8998565B2 (en) | 2015-04-07 |
| EP2527599A3 (en) | 2017-03-15 |
| EP2527599B1 (en) | 2020-07-01 |
| EP2527599A2 (en) | 2012-11-28 |
| CN102748136A (en) | 2012-10-24 |
| US20120260670A1 (en) | 2012-10-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102748136B (en) | The turbine blade stages in combustion gas turbine is used to carry out the equipment sealed | |
| JP6804305B2 (en) | Shroud hanger assembly | |
| US8206119B2 (en) | Turbine coverplate systems | |
| CN103291374B (en) | For the turbine blade of gas-turbine unit and method that platform is cooled down | |
| US8348603B2 (en) | Gas turbine inner flowpath coverpiece | |
| CN107013257A (en) | The arc-like sheet seal of the trough of belt of turbine | |
| CN103306748B (en) | Turbine interstage seal system | |
| CN104685157B (en) | The movable vane of turbogenerator | |
| CN103291373B (en) | Turbine bucket | |
| CN102536338A (en) | Cloth seal for turbo-machinery | |
| US10662795B2 (en) | Rotary assembly for a turbomachine | |
| JP2005098297A (en) | Method and apparatus to reduce seal friction within gas turbine engines | |
| CN106661954A (en) | Interstage seal housing optimization system in a gas turbine engine | |
| US20150167493A1 (en) | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine | |
| CN103510994B (en) | System having blade segment with curved mounting geometry | |
| US20130186103A1 (en) | Near flow path seal for a turbomachine | |
| CN103216274B (en) | There is the nearly flow path sealing member of axial elasticity arm | |
| US9382802B2 (en) | Compressor rotor | |
| CN102758794B (en) | There is the turbine inlet housing of solid box shell | |
| JP2013213492A (en) | Transition nozzle combustion system | |
| CN110337531A (en) | Turbine cylinder and for assemble with turbine cylinder turbine method | |
| JP6027445B2 (en) | Turbomachine rotor wheel | |
| US11156115B2 (en) | Guide vane arrangement for turbomachine | |
| EP1799967A1 (en) | Structure for separating the internal areas of a high pressure and a low pressure turbine | |
| US20160238020A1 (en) | Rotor disc |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240103 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York, United States Patentee before: General Electric Co. |